HyperCFD™ 2.5.0 ($150.00)
Supersonic and Hypersonic Rocket Analysis
Determine drag coefficient (Cd), center of pressure (Xcp), CN-alpha and Cm-alpha of supersonic and hypersonic rockets and re-entry vehicles. In addition, on a separate screen HyperCFD displays and plots CN-Body, CN-Fins, CN-Total and Cm-Total as a function of angle of attack (AOA) using up/down controls. HyperCFD uses empirical corrections to the modified Newtonian surface inclination method that allows excellent results from Mach 1.05 to Mach 20. Includes a wide variety of nose cone shapes and fin cross-sections. Nose cone shapes include, conical, elliptical, parabolic, power series Sears-Haack, tangent ogive and spherical segment. Fin cross-sections include single wedge, symmetrical double wedge, arbitrary double wedge, biconvex section, streamline section, round-nose section, and elliptical section fin shapes. HyperCFD is useful to determine supersonic rocket drag and Cp location for level 3 flights. Useful companion program to AeroCFD & 2D-WING™.

New Features
1) Temperature on the surface of the rocket relative to free-stream conditions.
2) Pressure and temperature can be output to a PLT file and read as a text file.
3) Cd estimation as a function of AOA based on Newtonian surface inclination theory.
4) Cd estimation and XCp estimation as a function of small angle of attack (1 to 2 degrees).
5) Cd estimation for decreasing cross-sectional components.

HyperCFD Results
Case #1: Re-Entry Vehicle

HyperCFD main screen displaying re-entry vehicle


HyperCFD re-entry vehicle pressure distribution


Case #2: Conical Nose Cone



Case #3: Missile With Fins

Hypersonic missile In free flight


HyperCFD main screen displaying hypervelocity missile


HyperCFD fin geometry screen for hypervelocity missile


HyperCFD Motor On/Off screen